US3139795A

US3139795A - Tandem loaded firing tubes

Info

Publication number: US3139795A
Application number: US197836A
Authority: US
Inventors: Altschuler Samuel
Original assignee: Individual
Current assignee: Individual
Priority date: 1962-05-24
Filing date: 1962-05-24
Publication date: 1964-07-07
Anticipated expiration: 1981-07-07

Description

y 7, 1964 s. ALTSCHULER TANDEM LOADED FIRING TUBES C5 Sheets-Sheet 1 Filed May 24, 1962 INVENTOR, 5 amual Ali-551114121" y 1964 s. ALTSCHULER TANDEM LOADED FIRING TUBES 5 Sheets-Sheet 2 Filed May 24, 1962 JNVEN TOR 5 arnue'L Auschuiar July 7, 1964 s. ALTSCHULER TANDEM LOADED FIRING TUBES 5 Sheets-Sheet 3 Filed May 24, 1962 INVENTOR. Samuel Alrschu ler BY J! 1 90:0010; a. J. fl xmh in /m 3,139,795 TANDEM LQADED FERENG TUBES Samuel Aitschnler, Woodland Hills, Calif assigner to the United States of America as represented by the Secretary of the Army Filed May 24, 1962, Ser. No. 197,836 2 Claims. (Cl. 89-137) This invention relates to improvements in multi-barrel weapons, particularly in a missile system adapted for mounting on aircraft.

The very high speed of modern aircraft has resulted in a drastic reduction in the period of time during which the aircraft weapons may be brought to bear on the target. Consequently, it has become increasingly important that weapons be developed capable of accurately delivering missiles at extremely high rates of fire. At the same time, the weight and size of the missile system must be kept within reasonable limits; Accordingly, it is a primary object of this invention to provide a novel missile system for aircraft having an extremely high rate of fire and having only moderate requirements as to weight and size.

It is an object of this invention to provide an automatic missile system in which a plurality of projectile holders are utilized.

It is a further object of this invention to provide a missile system with projectile holders each having a plurality of projectiles therein.

Another object of this invention is to provide a missile system with projectile holders each having a plurality of projectiles dischargeable in sequence.

It is another object of this invention to provide an ejectable sealing means for a projectile holder having a plurality of axially aligned projectiles.

Still another object of this invention is to provide a missile system utilizing a plurality of projectile holders arranged in a stationary cluster.

It is another object of this invention to utilize boosted rockets in an automatic missile system.

Other objects and advantages will become apparent as the description of the invention proceeds, taken in connection with the accompanying drawings in which:

FIGS. 1-3 show a firing sequence of one form of the invention, partially in section and partially in elevation.

FIG. 4 is a detailed sectional view of the bulkhead employed in the device of FIGS. 1-3.

FIG. 5 shows a second form of the invention, partially in section and partially in elevation.

FIG. 6 is a perspective view of an airplane equipped with a stationary cluster of firing tubes made in accord ance with the present invention.

FIG. 7 is a view in part schematic and in part perspective showing an arrangement for automatically discharging a pair of firing tubes made in accordance with the present invention.

FIG. 8 is a large scale sectional view of the snap ring which is also shown in FIG. 4.

FIG. 9 is a view in elevation of the snap ring of FIG. 8.

FIG. 10 is a large scale sectional view of the rear ignition structure of the launching tube shown in FIG. 5.

In the drawings, FIGS. 1-3, reference character 1 designates a cylindrical projectile holder or launching tube. Mounted in spaced axial alignment in the projectile holder are a forward rocket projectile 2 and a rear rocket projectile 3 separated by a bulkhead 4. Integral with the bulkhead is a spacing rod 5 which projects from the forward wall of the bulkhead and is fixed to the rear wall of the forward rocket by a shot start device such as shear pin 7. The spacing rod thus provides a first gas expansion chamber 8 between the forward rocket projectile and the bulk;

head 4 for accommodating a first booster charge 11. One end of the projectile holder is closed by a base plate 12 United States Patent O Patented July 7., 1954;-

having a threaded connection 13 with the projectile holder. integral with the base plate and extending forwardly thereof is a cylindrical igniter tube 14 which is connected to the rear wall of the rear rocket projectile by a shot start device such as shear pin 7. The igniter tube thus spaces the rocket 3 from base plate 12 to provide a second chamber 15 for accommodating a second booster charge 16. Extending rearwarclly of base plate 12 is an integral threaded lug 17 which projects through mounting plate 18. A nut 21 is mounted on the threaded lug to secure the launching tube 1 to the mounting plate. The igniter tube 14 includes a longitudinal igniter chamber 22 having a series of transverse flame ports 23 spaced longitudinally along the wall of the tube. The threaded lug 17 is counterbored to form a rear primer chamber 24 and a passageway 25. The passageway connects the rear primer chamber with the igniter chamber 22. A squib .26 is located in the rear primer chamber and the igniter tube contains a quantity of black powder.

Referring now particularly to FIGS. 4, 8 and 9, the bulkhead 4, in addition to the forwardly extending spacing rod 5, has an integral rearwardly depending cylindrical skirt 28. The bulkhead has a diameter slightly less than the internal diameter of the launching tube 1 so that there is a clearance between the skirt 28 and the wallet the launching tube. An annular groove 31 on the periphery of the bulkhead mates with an annular groove 32 in the internal wall of the launching tube. A snap ring 33 having a cam surface 34 is seated in annular groove 31 and in normal position extends into annular groove 32. The snap ring cam surface 34 mates with a cam surface 35 provided in the forward wall of annular groove 32. The snap ring is provided with longitudinal gas slots as shown at 36. The bulkhead has provided in its forward wall an annular chamber 37 separated from the first booster charge 11 by a sealing annulus 38 which has perforations therethrough as at 41. There is a squib chamber 42, containing squib 43, located radially outwardly of annular chamber 37 and connected thereto by passage 44.

Surrounding the launching tube 1 adjacent the annular bulkhead groove 31 is a metal contact ring 45. Between the contact ring and the launching tube is an insulating ring 46 which has an inwardly extending collar 47 projecting through a bore 48 in the Wall of the launching tube. Firing pin 51 is connected to contact ring 45 and projects inwardly through the insulating collar 47 into electrical contact with the squib 43. Annular chamber 37 contains a suitable primer charge such as black powder.

Referring again to FIGS. 1-3, it will be noted that the

rockets

2 and 3 are of the spin stabilized type, each being provided with a pair of

motor nozzles

52 and 53, and each having a rotating band 54 for cooperation with the rifting 55 in the launching tube.

The operation of the launching tube 1 shown in FIGS. 1-4 is as follows: The forward rocket projectile 2 is fired by completing a circuit through the contact ring 45 and the firing pin 51 which ignites the squib 43 and, in turn, the primer charge in the annular chamber 37, and the first booster charge 11. The ignited first booster charge builds up gas pressure to a predetermined amount breaking the shear pin 7, which secures the rocket to the rod 5 and also ignites the rocket motor through the

motor nozzles

52 and 53. The released projectile is discharged through the tube muzzle. The recoil reaction developed in firing the forward rocket projectile is transmitted to the launching tube 1 by the snap ring 33. The launching tube is reinforced at this section by the contact ring 45. A gas pressure amounting to approximately 50 percent of the peak pressure developed by the first booster charge is built up (arrows FIG. 8) behind the bulkhead through the slots 36 in the snap ring 33. When the forward rocket 89 projectile has left the muzzle and the gas pressure in front of the bulkhead has consequently dropped, the pressure behind the bulkhead will collapse the snap ring by forcing the cam surface 34 of the snap ring against the cam surface 35 in the wall of the launching tube. When the snap ring has collapsed, the slots 36 are substantially closed,

and the bulkhead is then ejected. The squib 26 located in the rear primer chamber 24 may then be ignited. This is immediately followed by ignition of the black powder in the igniter tube and the second booster charge 16 through flame ports 23, and then the rocket motor through

motor nozzles

52 and 53. When the gas pressure rises to a predetermined level the shear pin 7 at the end of igniter tube 14 is severed and the rear projectile is discharged through the muzzle of the launcher tube.

FIG. 6 shows a multiple launcher tube installation on an airplane 61. A plurality of launching tubes 1 are inclosed in a stationary cluster housing 62 which is fixed to the belly of the plane.

The circuit diagram of FIG. 7 illustrates schematically one method of automatically firing a stationary cluster of launcher tubes. The principle elements are: a source of current 63, a plurality of launching tubes (only two shown) 64 and 65, a selector switch 66 having fixed contacts 67, 68, 69, 70 and a movable contact 73, and an electric motor 74 for driving the movable contact.

The source of current is connected by wire 75 to the movable contact. Each fixed contact is connected either to a forward or rear igniter of one of the launching tubes. Thus, contact 67 is connected to the forward igniter of launching tube 64 by wire 76, contact 68 is connected to the forward igniter of launching tube 65 by wire 77, contact 69 is connected to the rear igniter of launching tube 64 by wire 78, and contact 70 is connected to the rear igniter of launching tube 65 by wire 79. The launching tube barrels together with wires 80 and 81 provide the return line to the power source.

In operation the motor 74 is actuated, rotating the movable contact 73 in a clockwise direction. When the movable contact closes on fixed contact 67 the circuit to the forward igniter of launcher tube 64 is completed and the forward round in the launcher tube is fired. The rotation of the movable contact next closes on fixed contact 68 which completes a circuit to the forward igniter of launcher tube 65 and the forward round in that launcher tube is fired. The movable contact next closes on fixed contact 69 which completes a circuit to the rear igniter of launcher tube 64 and the rear round in the launcher tube is fired. Finally, the movable contact closes on fixed contact 70 which completes the circuit to the rear igniter of the launcher tube 65 and the rear round in that launcher tube is fired. The

launcher tubes

64 and 65 are thus completely discharged.

It is clear that while only two launcher tubes are shown in FIG. 7, the number of launcher tubes may be increased to any desired number by adding fixed contacts and connecting them to the igniters of the launcher tubes in the same manner. If it is desired to completely discharge the launcher tubes successively, it is evident that this may be accomplished by connecting the rear igniter of launcher tube 64 to fixed contact 68 and forward igniter of launcher tube 65 to fixed contact 69. Launcher tube 64 will thus be completely discharged before the forward round in launcher tube 65 is fired.

In the embodiment shown in FIG. 5, the aft end of the projectile holder or launching tube 1 which incloses the second chamber 15 is of somewhat reduced diameter. Between the reduced portion of the launching tube and that portion of the launching tube surrounding the rear rocket projectile 3 the launching tube wall forms an annular sealing shoulder 84. The second booster charge 16 is packaged in a booster charge can 85. The wall of the booster charge can 85 snugly engages the wall of the launching tube, and at its forward end follows the contour of the interna W l of the launching tube over the sealing shoulder 84 and surrounds the aft end of the rear rocket projectile 3. The rear rocket projectile has an annular groove 86 into which the forward edge 87 of the booster charge can is crimped to form a shot start device. A peripheral portion 88 of the end wall 91 of the rear rocket projectile is seated against the booster can at the annular sealing shoulder 84.

Referring now to FIG. 10, one end of the prejectile holder is closed by a base plate 12 having a threaded connection 13 with the projectile holder. Located axially in the second booster chamber 15 is an igniter tube 14 which extends through bore 92 in the bottom wall 93 of the booster charge can 85, bore 94 in the base plate, and bore 95 in the mounting plate 18. Flange 96, which is integral with the igniter tube 14, abuts the bottom wall 93 of the booster charge can around the bore 92. The threaded end 17 of the flame tube which projects through the mounting plate has a nut 21 mounted thereon to draw the flange 96, the bottom wall 93, and the base plate 12 toward the mounting plate. The igniter tube is provided with a longitudinal flame passage and a series of transverse flame ports 23 spaced longitudinally along the wall of the flame tube.

Forward of sealing shoulder 84 the wall of the launching tube is provided with an externally thickened portion or reinforcing ring 97. An annular groove 98 is pro vided in the internal wall of the launching tube at the thickened portion. With the rear rocket projectile in posi- 7 tion, the annular groove is adjacent the rotating band 54 on the projectile. An O-ring 100 is located in the annular groove 98 and is of such diameter that it extends into sealing engagement with the rotating band.

The forward rocket projectile 2 is provided with annular stop groove 86. A shot start device, in the form of shear pins 102 in the wall of the launching tube extend into the annular stop groove 86 to retain the forward rocket projectile in the desired spaced relation to the rear rocket projectile. The space between the forward and rear rocket projectiles constiutes a first gas expansion chamber 8 for accommodating the first booster charge 11.

Surrounding the launching tube adjacent the first chamber is an annular igniter 103. The igniter includes a metal contact ring 164 having inwardly extending flanges 105, forming an igniter chamber 106. The contact ring is insulated from the launching tube by a pair of insulating rings 107 and 108 positioned between the flanges and the wall of the launching tube.

chamber. The igniter chamber 106 communicates with the first chamber 8 by means of a series of flame ports 113 bored through the wall of the launching tube.

The launching tube shown in FIG. 5 operates as follows: The forward rocket projectile is fired by completing a circuit through contact ring 104 which ignites the squib 111 and, in turn, the primer charge 112 and the first booster charge 11. The ignited first booster charge 11 builds up gas pressure to a predetermined level breaking shear pins 102 and also igniting the rocket motor through the

motor nozzles

52 and 53. The ogive 101 of the rear rocket projectile and the

seals

84 and 100 prevent premature ignition of the second booster charge 16. It will be noted that as pressure increases on the ogive 101 the effectiveness of the seals increases. When the forward rocket projectile has cleared the muzzle of the launcher tube, the rear rocket projectile may be fired as described previously. 7

From the foregoing, it is apparent that a light-weight rapid-fire automatic rocket weapon has been developed that is particularly suitable for mounting on aircraft.

Since certain changes may be made in the structures described without departing from the scope of the invention, it is intended that all matter contained in the above description, or shown in the accompanying drawings, shall be interpreted as generally illustrative and not in a strictly limiting sense.

A squib 111 and a primer charge of black powder 112 are located in the igniter What is claimed is:

1. In a rocket weapon, a plurality of projectile holding tubes, each of said projectile holding tubes having a plurality of axially aligned rocket projectiles therein, said rocket projectiles spaced in said projectile holding tubes to provide gas expansion chambers at the rear of each of said rocket projectiles, a propellent charge in each of said gas expansion chambers, bulkheads positioned between successive gas expansion chambers for isolating said chambers one from the other, each said bulkhead comprising a rearwardly depending skirt and a spacing rod extending forwardly from the skirt, said rod having its rearward end integral with the forward wall of said bulkhead, the forward end of the rod being detachably fixed to the rearward wall of the forward rocket, said bulkhead having a diameter slightly less than the internal diameter of each projectile holding tube, whereby a clearance is formed between said skirt and the wall of said tube, said spacing rod defining a first gas expansion chamber between the forward rocket and said bulkhead, resilient locking means on each of said bulkheads preventing rearward movement of said bulkheads, said locking means responsive to positive pressure aft of said bulkhead to release said bulkhead for forward movement and ejection, ignition means for each of said rocket projectiles, and contact means for sequentially actuating said ignition means to discharge said projectile holding tubes.

2. In a rocket weapon, a plurality of projectile holding tubes, each of said projectile holding tubes having a plurality of axially aligned rocket projectiles therein, said rocket projectiles spaced in said projectile holding tubes to provide gas expansion chambers at the rear of each of said rocket projectiles, a propellant charge in each of said gas expansion chambers, said gas expansion chambers being sealed from each other so' that the ignition of one of said propellent charges will not ignite the other of said charges, the means for isolating said chambers from each other comprising a bulkhead positioned between the successive gas expansion chambers, locking means responsive to piston pressure aft of said bulkhead to release said bulkhead for forward movement and ejection from its tube, said locking means comprising a snap ring having longitudinal gas slots in its inner peripheral surface, there being a first annular groove in the outer periphery of said bulkhead and a second annular groove in the internal wall of said tube, and mating with said first annular groove, said snap ring having a cam surface and normally extending into said second annular groove, whereby gas pressure developed in firing said forward rocket and transmitted through said slots in said snap ring and behind said bulkhead will move said bulkhead forward in said tube and collapse said snap ring into said first annular groove to permit ejection of said bulkhead from said tube by said gas pressure, separate ignition means for each of said propellent charges, and contact means for selec tively actuating said ignition means to discharge said projectile holding tubes.

References Cited in the file of this patent UNITED STATES PATENTS 2,099,993 Tauschek Nov. 23, 1937 2,313,030 Tauschek Mar. 2, 1943 2,644,364 Nass July 7, 1953 2,780,143 Graham Feb. 5, 1957 2,920,533 Musser Jan. 12, 1960 2,930,288 Jonah Mar. 29, 1960 2,938,430 Pion May 31, 1960

Claims

1. IN A ROCKET WEAPON, A PLURALITY OF PROJECTILE HOLDING TUBES, EACH OF SAID PROJECTILE HOLDING TUBES HAVING A PLURALITY OF AXIALLY ALIGNED ROCKET PROJECTILES THEREIN, SAID ROCKET PROJECTILES SPACED IN SAID PROJECTILE HOLDING TUBES TO PROVIDE GAS EXPANSION CHAMBERS AT THE REAR OF EACH OF SAID ROCKET PROJECTILES, A PROPELLANT CHARGE IN EACH OF SAID GAS EXPANSION CHAMBERS, BULKHEADS POSITIONED BETWEEN SUCCESSIVE GAS EXPANSION CHAMBERS FOR ISOLATING SAID CHAMBERS ONE FROM THE OTHER, EACH SAID BULKHEAD COMPRISING A REARWARDLY DEPENDING SKIRT AND A SPACING ROD EXTENDING FORWARDLY FROM THE SKIRT, SAID ROD HAVING ITS REARWARD END INTEGRAL WITH THE FORWARD WALL OF SAID BULKHEAD, THE FORWARD END OF THE ROD BEING DETACHABLY FIXED TO THE REARWARD WALL OF THE FORWARD ROCKET, SAID BULKHEAD HAVING A DIAMETER SLIGHTLY LESS THAN THE INTERNAL DIAMETER OF EACH PROJECTILE HOLDING TUBE, WHEREBY A CLEARANCE IS FORMED BETWEEN SAID SKIRT AND THE WALL OF SAID TUBE, SAID SPACING ROD DEFINING A FIRST GAS EXPANSION CHAMBER BETWEEN THE FORWARD ROCKET AND SAID BULKHEAD, RESILIENT LOCKING MEANS ON EACH OF SAID BULKHEADS PREVENTING REARWARD MOVEMENT OF SAID BULKHEADS, SAID LOCKING MEANS RESPONSIVE TO POSITIVE PRESSURE AFT OF SAID BULKHEAD TO RELEASE SAID BULKHEAD FOR FORWARD MOVEMENT AND EJECTION, IGNITION MEANS FOR EACH OF SAID ROCKET PROJECTILES, AND CONTACT MEANS FOR SEQUENTIALLY ACTUATING SAID IGNITION MEANS TO DISCHARGE SAID PROJECTILE HOLDING TUBES.